Aircraft flight control surface actuation system communication architecture

Abstract

A flight control surface actuation system includes a plurality of smart actuators to move aircraft flight control surfaces between extended and retracted positions. The system includes a high availability network between the flight control avionics and the smart actuators, and between each of the smart actuators. The system configuration allows network nodes associated with each smart actuator to monitor and control one another, under higher level control of the aircraft flight control avionics, to provide multiple levels of health monitoring, control, and shutdown capability.

Description

CROSS-REFERENCES TO RELATED APPLICATIONS [0001] This application claims the benefit of U.S. Provisional Application No. 60 / 604,249, filed Aug. 24, 2004.TECHNICAL FIELD [0002] The present invention relates to flight surface actuation and, more particularly, to the communication architecture for a flight control surface actuation system. BACKGROUND [0003] Aircraft typically include a plurality of flight control surfaces that, when controllably positioned, guide the movement of the aircraft from one destination to another. The number and type of flight control surfaces included in an aircraft may vary, but typically include both primary flight control surfaces and secondary flight control surfaces. The primary flight control surfaces are those that are used to control aircraft movement in the pitch, yaw, and roll axes, and the secondary flight control surfaces are those that are used to influence the lift or drag (or both) of the aircraft. Although some aircraft may include additional ...

AI Technical Summary

Benefits of technology

[0008] The present invention provides a flight control surface actuation system that uses smart actuators, and includes a high availability network between the flight control avionics and the smart actuators and between each of the smart actuators. This configuration provides multiple levels of health monitoring, control, and shutdown capability.

[0009] In one embodiment, and by way of example only, an aircraft flight control system includes a plurality of independent communication channels, a flight control avionics channel, a plurality of actuators, and a plurality of remote electronic control units. The flight control avionics channel is operable to supply flight control surface position commands representative of a commanded flight control surface position via each of the independent communication channels. Each actuator is adapted to couple to an aircraft flight control surface, is coupled to receive actuator position commands, and is operable, upon receipt of the actuator position commands, to move to an actuator position corresponding to the commanded flight control surface position. The remote electronic control units are disposed remote from the flight control avionics, and each is associated with one of the plurality of actuators. Each remote electronic control unit is coupled to receive the flight control surface position commands supplied from each of the independent actuator control channels and is operable, in response thereto, to supply the actuator position commands to its associated actuator. Each remote electronic control unit is also coupled to receive one or more signals representative of operability of one or more of the plurality of actuators and one or more other remote electronic control units and is operable, in response thereto, to determine to whether one or more of the plurality of actuators are operating improperly and whether one or more of the other remote electronic control units are operating improperly.

[0010] In another exemplary embodiment, an aircraft flight control system includes a plurality of independent communication channels, a flight control avionics channel, a plurality of communication hubs, a plurality of remote electronic control units, and a plurality of actuators. The flight control avionics channel is operable to supply flight control surface position commands representative of a commanded flight control surface position via each of the independent communication channels. Each communication hub is coupled to receive the flight control surface position commands supplied from one of the independent channels and is operable to supply the received flight control surface position commands. Each remote electronic control unit is coupled to one of the communication hubs to receive the flight control surface position commands supplied therefrom, and is operable, upon receipt of the flight surface position commands, to supply actuator position commands. Each actuator is adapted to couple to an aircraft flight control surface, is coupled to receive the actuator position commands from one of the actuator control units, and is operable, upon receipt of the actuator position commands, to move to an actuator position corresponding to the commanded flight control surface position.

[0011] Other independent features and advantages of the preferred flight control surface actuation control system will become apparent from the following detailed description, taken in conjunction with the accompanying drawings which illustrate, by way of example, the principles of the invention.

Problems solved by technology

Though unlikely, it is postulated that a flight control surface actuator could become inoperable.

Although the flight control surface actuation systems that include hydraulic, pneumatic, and / or electromechanical actuators are generally safe, reliable, and robust, these systems do suffer certain drawbacks.

Namely, these systems can be relatively complex, can involve the use of numerous parts, can be relatively heavy, and may not be easily implemented to provide sufficient redundancy, fault isolation, and / or system monitoring.

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